METRO III – ICAO ANNEX 8 PART C – TAKEOFF PERFORMANCE DRY, BLEED AIR ON CONTENTS ITEM
PAGE
Takeoff Power Check Chart ............................................................................................................... 4C-1 Maximum Takeoff Weight Limitation Chart ........................................................................................ 4C-3 Takeoff Speed Schedules .................................................................................................................. 4C-4 Distance to Accelerate to V1 and Stop ............................................................................................. 4C-11 Single Engine Takeoff Distance to 35 Foot Height .......................................................................... 4C-12 Takeoff Flight Path Distance to 1500 Foot Height ........................................................................... 4C-14 Second Segment Climb Gradient ............................................................................................ 4C-18 Close In Obstacle Clearance .................................................................................................. 4C-19 Second Segment Acceleration Distance ................................................................................. 4C-20 Third Segment Climb Gradient ................................................................................................ 4C-22 Distant Obstacle Clearance .................................................................................................... 4C-23 Single Engine Takeoff Run Distance ............................................................................................... 4C-24 Two Engine Rate of Climb at V50. .................................................................................................... 4C-26
FAA APPROVED: MAY 22/89 REVISED: MAR 18/92
PERFORMANCE
4C-i 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-ii 8AC
PERFORMANCE
MANUFACTURER'S DATA ISSUED: MAY 22/89
TAKEOFF POWER CHECK CHART - DRY, BLEED AIR ON ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER .............TAKEOFF (DRY) RPM ......................................100% MAX ALLOWABLE EGT.. ..65O”C GEN LOAD .................300 AMPS BLEED AIR ..............................ON ENG ANTI-ICE ........ SEE GRAPH SPEED ..............................STATIC
GIVEN:
OAT = 0°C PRESSURE ALTITUDE = 2,000 FEET ENGINE ANTI-ICE SYSTEM - OFF OBTAIN: ENGINE TORQUE = 91.3 PERCENT
l
l
MAXIMUM
OAT WITH ENGINE ANTI-ICE ON IS 5°C.
REFERENCE EGT IS THE EGT OBTAINED WHEN REQUIRED ENGINE TORQUE IS SET IN ACCORDANCE WITH THIS CHART AND MUST NOT EXCEED 650°C.
I-
100
60
-40
-30
-20
7” -10
0
10 OAT (OC)
20
30
40
50
OFF
ON ENGINE ANTI-ICE SYSTEM
D 0 D z z m x 00
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-2 8AC
PERFORMANCE
FAA APPROVED: MAY DATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
METRO III -ICAO ANNEX 8 MAXIMUM TAKEOFF WEIGHT LIMITATION ASSOCIATED
CONDITIONS:
POWER .. .... .... ... ................ TAKEOFF (DRY) GEN LOAD ......._.........................300 AMPS BLEED AIR .................................. .. ..... ... .. ON ENG ANTI-ICE . .._..._.......OFF (SEE NOTE) GEAR ........... ... .. ..... ....... DOWN (TAKEOFF) UP (SECOND AND THIRD SEGMENT) FLAPS .. ... ..... ........................ l/4 (TAKEOFF) UP (ENROUTE)
CHART - DRY, BLEED AIR ON 7
NOTE l
l
l
REDUCE TAKEOFF WEIGHT BY 1,235 POUNDS WITH ENGINE ANTI-ICE ON. MAXIMUM
OAT WITH ENGINE ANTI-ICE
(660 kg)
ON IS 5°C.
THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE V 1.
EXAMPLE: GIVEN:
OAT = 26°C PRESSURE ALTITUDE = 5,600 FEET OBTAIN: TAKEOFF WEIGHT = 11,750 POUNDS (5330 kg)
17
16
FAA APPROVED: MAY 22f89
FIGURE 4C-2 PERFORMANCE
4c-4 8AC
5 D
FAA APPROVED: MAY 22189
METRO III -ICAO ANNEX 8
FIGURE 4C-3 PERFORMANCE
c
:: 03
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FIGURE 4C-3 (continued) PERFORMANCE
=: z
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8 is
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METRO III -ICAO ANNEX 8
5'2
kc3e-mz zl-, t;i'i;k L -
FAA APPROVED: MAY 22l89
4c-5 8AC
METRO III – ICAO ANNEX 8
THIS PAGE LEFT BLANK INTENTIONALLY
4C-6 8AC
PERFORMANCE
FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89
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4C-8 8AC
FAA APPROVED: MAY 22189
METRO Ill -ICAO ANNEX 8
FIGURE 4C-3 (continued) PERFORMANCE
k 0
PERFORMANCE
ANNEX 8
FIGURE 4C-3 (continued)
METRO III -lCAO
FAA APPROVED: MAY 22/89
4c-9
8AC
TAKEOFF SPEED SCHEDULE (KIAS) - DRY, BLEED AIR ON 1CAUTION
piiz%ic1 6
. REFER
OUTSIDE
I
PRES RLT (FT)
-10
iRD55 HT IKG 1
1
. TAKEOFF IN TEMPERATURE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID. STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION ONLY.
0
I
RIR
4C-2
TEMPERRTURE 10
I
TO FiGURE
FOR MAXIMUM
TAKEOFF
WEIGHTS.
[‘Cl 20
I
PERMISSIBLE
UO
I
I
I
7257 7000 6800 6600 u 6200 600
5800 5600 5uoo 5200 5000 U800 4600
110
Jios
107 106 -1011 103 101 -100 100 100 100 100 100 100
120 117 115 113 111 108 106 1011 103 102 102 101 100 100
1 I 6800 6600 6UOO 6200 7001
6000
5800 5600 51100 5200
6001
7257 7000 6800 6600 6400 6200 6000 5600 5600
51100 5200 5000 11800 4600
119 118 116 115 113 112 110 109 109 109 109 109 110
128 126 25 :24 123 121 120 119 120 120 120 121 121 123
111
I 107 106 104 103 101 100 100 100 100 100 100 100
116 11’4 112 110 106 106 105 104 103 103 102 101
116 115 113 112 110 109 109 109 109 109 109 110
125 123 122 121 120 119 119 119 120 120 121 121
I
I
I
I
I
I
I
I
1
I
I
I
_ 110 108 107 -,106 1011 103 101 100 100 -100 100 100 -100 100
120 116 116 114 111 109 107 105 104 103 103 102 101 100
119 118 116 115 113 112 110 109 109 109 109 109 109 110
108 107 106 104 103 101 100 100 100 100 100 100 100
118 117 115 112 110 106 106 105 104 1011 103 102 101
118 125 116 121 115 123 113L122 112 121 110 120 109 119 109 119 109 119 109 120 109 120 109 120 110 121
I
104 103 101 100 100 100 100 100 100 100
113 111 109 107 106 106 105 1011 1ou 103
I
I
I
I
113 112 110 109 109 109 109 109 109 110 I
122 120 119 118 119 119 119 120 120 120 I
112 109 107 107 106 105 105 10’4 103
112 110 109 109 109 109 109 109 110
120 119 118 119 119 119 120 120 120
100 100 100 100 100 100 100
109 108 108 107 106 105 105
109 109 109 109 109 109 110
100 100 100 100 100 100 100 I
127 126 125 123 106 115 115 123 122 104 113 113 122 121 103 111 112 121 120 101 l( ~slllolll9llollllolllo~ll9~ 119 100 lL-1~lln9l1l~11n~llnRllflalllnl ii~‘i~~lio;llo9l~~~~~oo~lo9~lo~~~~~~ 119 100 106 iij, 120 100 105 109 119 10 0 107 109 119 120 100 1011 109 119 10 0 106 109 119 12-O Iloollo~llo9ll2olloo 105 109 119 121 100 103 109 120 100 105 109 120 121 100 102 110 121 100 1011 110 120
103 101 100 100 100 100 100 lo0 100
I
I
116 116 118 119 119 119 120
109 109 108 109 107 109 107 109 106 109 105 109 105 110 I
I
I
118 118, 118 119 119 119 120 I
I
I
I
I
I
I
100 100 100 100 100
zm
55
-I 3 0
I
109 109 109 109 109
109 109 109 109 110
116 116 117 116 119
i
I
I
I
I
I
I
I
I
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I
I
I
I
I
I
I
1 100 100 100 100 100
108 108 107 106 106
109 109 109 109 110
118 19 :19 119 120
I:: 100 100
:oslmll4 109 109 109 110
117 118
100 100 100 100 100
109 109 108 107 107
109 109 109 109 110
118 116 119 119 119
100 100 100
109 109 109
115 116 117
109 109 110
I
0 D 0 D z z
m x 00
METRO III -ICAO ANNEX 8 DISTANCE
TO ACCELERATE
ASSOCIATED
TO V, AND STOP - DRY, BLEED AIR ON
CONDITIONS:
EXAMPLE:
POWER .............. ... .... .... ....TAKEOFF (DRY) GEN LOAD .. ... ..... ....................... 300 AMPS BLEED AIR .. .... .. .. .... ... ............................. ON ENG ANTI-ICE . .... ........ .OFF (SEE NOTE) RUNWAY .. ............ DRY, HARD SURFACE FLAPS ...... .... .... ......................................... 114 DECISION SPEED .. ... .V 1 (FIGURE 4X3) NOSE WHEEL STEERING ...ON OR OFF
GIVEN:
OAT = 15°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 15,000 POUNDS (6805 kg) HEADWIND = 6 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) OBTAIN: V 1 SPEED = 109 KIAS ACCELERATE -STOP DISTANCE = 4,900 FEET (1495 m) INCREASE ACCELERATE - STOP DISTANCE PERCENT WITH ENGINE ANTI-ICE ON.
l
MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 462.
MAXIMUM
l
OAT WITH ENGINE ANTI-ICE
BY 4.1
ON IS 5°C.
r GROSS 7
WEIGHT (1000 kg) 6
5 14
4
13
12
40
-20
0
20
OAT (OC)
FAA APPROVED: MAY 22l%9
40
60
16 GROSS
15
14 WEIGHT
13
12 (1,000
FIGURE 4C-4 PERFORMANCE
11
10
POUNDS)
0 WIND
10
20 (KNOTS)
30
0
1
RUNWAY SLOPE (PERCENT)
2
SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT - DRY, BLEED AIR ON
ENGINE
ANTI-ICE
EFFECTS
(METERS) 190
150
200
250
3c)o
8,00C
7,000
6,000
2,000
1,000
S.L. 0
200
400
600
800
1,000
(FEET) INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4C-12 8AC
4C-5
PERFORMANCE
FAA APPROVED:
MAY 22/89
METRO III -ICAO SINGLE
ENGINE
TAKEOFF
ASSOCIATED
DISTANCE
TO 35 FOOT
ANNEX 8
HEIGHT
- DRY, BLEED
AIR ON
EXAMPLE:
CONDITIONS:
............................. TAKEOFF (DRY) POWER .300 AMPS GEN LOAD ................................ ON BLEED AIR .............................................. ENG ANTI-ICE ............ OFF (SEE GRAPH) RUNWAY ............... DRY, HARD SURFACE FIGURE 4C-3 V , SPEED ............................ .......................... FIGURE 4C-3 V R SPEED.. FIGURE 4C-3 V 2 SPEED ............................ l/4 FLAPS ....................................................... NOSE WHEEL STEERING ...O N OR OFF
GIVEN:
OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) Vi SPEED = 109 KIAS V k SPEED = 109 KIAS Vp SPEED = 113 KIAS TAKEOFF DISTANCE = 6,500 FEET (1980
OBTAIN:
kg)
m)
NOTE FOR TAKEOFF FIELD LENGTH ENGINE TAKEOFF DISTANCES ENGINE TAKEOFF DISTANCES
MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FlGURE4C-2.
GROSS
WEIGHT
7
-40
-20
0
20
OAT (OC)
40
60
16
GROSS
15
(1000 kg)
6
14
13
WEIGHT
DETERMINATION, SINGLE ARE LONGER THAN TWO FACTORED BY 1.15.
5
12
(1.000
11
10
POUNDS)
0 10 20 30 WIND (KNOTS)
0
1 2 RUNWAY SLOPE (PERCENT)
FIGURE 4C-5 (continued) FAA APPROVED: MAY 22l89
PERFORMANCE
4c-13 8AC
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON An estimate of the horizontal distance required to clear an obstacle up to 1,500 feet above the runway, or the required climb gradient to clear an obstacle along the takeoff flight path, may be obtained by using Figures 4C-5 through 4C-10. The takeoff flight path is as follows:
START OF TAKEOFF ROLL
AFTER TAKEOFF, GEAR IS RETRACTED
MAINTAIN V2 CLIMB TO 400 FEET WITH 1/4 FLAPS
ACCELERATE TO VYSE, RETRACT FLAPS AT V2 +5 KNOTS AND FEATHER INOPERATIVE PROPELLER
VYSE
V2
400 FT
V2 VR
SINGLE ENGINE TAKEOFF FLIGHT PATH TO 35 FOOT HEIGHT (FIGURE 4C-5)
REDUCE POWER TO MCP AND CONTINUE CLIMB TO 1,000 FEET
END OF FLIGHT PATH
TWO ENGINE TAKEOFF WITH ENGINE FAILURE RECOGNIZED AT V1, FLAPS 1/4
1,000 FEET
35 FT SECOND SEGMENT CLIMB (FIGURES 4C-6 AND 4C-7)
SECOND SEGMENT ACCELERATION (FIGURE 4C-8)
THIRD SEGMENT CLIMB (FIGURES 4C-9 AND 4C-10 )
The takeoff flight path consists of four phases defined as follows: 1. SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4C-5). Both engines are assumed to operate normally to speed V1 where one engine is recognized as failed and the takeoff is continued on one engine. This phase ends when the airplane reaches 35 feet above the runway surface at V2. 2. SECOND SEGMENT CLIMB (FIGURES 4C-6 and 4C-7). The second segment climb is a constant V2 climb starting at a height of 35 feet above the runway surface and ends at a height of 400 feet above the runway. The landing gear is fully retracted at the start of this phase, flaps remain at 1/4, and the propeller on the inoperative engine is windmilling in the NTS mode. Figures 4C-6 and 4C-7 present net climb gradient.
4C-14 8AC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON (continued) 3. SECOND SEGMENT ACCELERATION (FIGURE 4C-8). This phase is an acceleration at 400 feet height from V2 to VYSE. The flaps are retracted at V2 +5 knots, the propeller on the inoperative engine is feathered, and takeoff power is maintained until VYSE is obtained. 4. THIRD SEGMENT CLIMB (FIGURE 4C-9 and 4C-10). The third segment climb is at VYSE with maximum continuous power set. It starts at 400 feet and is completed at 1500 feet above the runway surface. Figures 4C-9 and 4C-10 present net climb gradient. The following are three examples to illustrate the use of the flight path data charts. EXAMPLE 1 – DETERMINATION OF TOTAL DISTANCE TO 1500 FEET Given:
OAT = 10°C Airport Pressure Altitude = 2,000 feet Gross Weight = 14,000 pounds (6350 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off
Obtain: 1. Single EngineTakeoff Distance to 35 Foot Height (Figure 4C-5) =6,500 feet (1980 meters). 2. Second Segment Climb Gradient (Figure 4C-6) = 3.4%. 3. Enter Figure 4C-7 at 400 feet and proceed to 3.4%. Obtain 10,700 feet (3260 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4C-8) = 6,200 feet (1890 meters) to accelerate from V2 to VYSE. 5. Third Segment Climb Gradient (Figure 4C-9) = 3.6%. 6. Enter Figure 4C-10 at 1500 feet and proceed to 3.6%. Obtain 30,250 feet (9220 meters) to climb from 400 feet to 1500 feet. 7. Total Distance is: 6,500 feet (1980 10,700 feet (3260 6,200 feet (1890 30,250 feet (9220 53,650 feet (16350
FAA APPROVED: MAY 22/89
meters) to 35 feet meters) to 400 feet meters) to accelerate to VYSE meters) to 1500 feet meters) (8.83 nautical miles)
PERFORMANCE
4C-15 8AC
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON (continued) EXAMPLE 2 – CLOSE IN OBSTACLE CLEARANCE Given:
OAT = 10°C Airport Pressure Altitude = 2,000 feet Gross Weight = 14,000 pounds (6350 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 350 feet* (107 meters) Obstacle Distance From Brake Release = 20,500 feet (6250 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4C-5) = 6,500 feet (1980 meters). 2. Obstacle horizontal distance from the 35 foot height point equals the total obstacle distance minus the distance to 35 feet height. 20,500 – 6,500 = 14,000 feet (4265 meters). 3. Second Segment Climb Gradient (Figure 4C-6) = 3.4%. 4. To obtain the required climb gradient to clear the close in obstacle, enter Figure 4C-7 at 350 feet* and at 14,000 feet distance. Obtain required climb gradient of 2.25%. 5. Since the required gradient, 2.25%, is less than the actual gradient, 3.4%, this obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 350 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4C-7.
4C-16 8AC
PERFORMANCE
FAA APPROVED: MAY 22/89
METRO III – ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – DRY, BLEED AIR ON (continued) EXAMPLE 3 – DISTANT OBSTACLE CLEARANCE Given:
OAT = 10°C Airport Pressure Altitude = 2,000 feet Gross Weight = 14,000 pounds (6350 kg) Headwind = 20 knots Runway slope = 1 percent (uphill) Engine Anti-ice off Obstacle Height = 700 feet* (213 meters) Obstacle Distance from Brake Release = 38,400 feet (11705 meters)
Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4C-6) = 6,500 feet (1980 meters). 2. Second Segment Climb Gradient (Figure 4C-6) = 3.4%. 3. Enter Figure 4C-7 at 400 feet and proceed to 3.4%. Obtain 10,700 feet (3260 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4C-8) = 6,200 feet (1890 meters) to accelerate from V2 to VYSE. 5. The horizontal distance from the end of the second segment acceleration to the obstacle equals 38,400 – 6,500 – 10,700 – 6,200 = 15,000 feet (4570 meters). 6. Enter Figure 4C-10 at 700 feet* height and 15,000 feet distance. Obtain required gradient of 2.0%. 7. The Third Segment Climb Gradient (Figure 4C-9) = 3.6%. 8. Since the required gradient, 2.0%, is less than the actual gradient of 3.6%, the obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 700 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4C-10.
FAA APPROVED: MAY 22/89
PERFORMANCE
4C-17 8AC
METRO III -ICAO TAKEOFF
FLIGHT
PATH
DISTANCE
TO 1500 FOOT
HEIGHT
ANNEX 8 (continued)
SECOND SEGMENT CLIMB GRADIENT - DRY, BLEED AIR ON
FEET 0 w . 3.4 PERCENT
GRADIENT
-6
-2
0
2
4
NET CLIMB
GRADIENT
6 (PERCENT)
6
10
12
14
FIGURE 4C-6 4C-18 8AC
PERFORMANCE
FAA APPROVED: MAY 22189
3 Ib Gi 71
TAKEOFF
FLIGljT
PATH
DISTANCE
TO 1500 FOOT
HEIGHT
(continued)
CLOSE IN OBSTACLE CLEARANCE - DRY, BLEED AIR ON ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER .............I........TAKEOFF (DRY) GEN LOAD ..................... ..... 300 AMPS BLEED AIR ... ... ................... .... .......... ON ENG ANTI-ICE .................ON OR OFF CLIMB SPEED .....V2 (FIGURE 4C-3) GEAR ............................. ... ................. UP FLAPS ................................................ 114
GIVEN:
OBSTACLE HEIGHT ABOVE THE RUNWAY SURFACE OBSTACLE HORlZONTAL DISTANCE FROM 35 FOOT POINT = 14,000 FEET (4265 m) OBTAIN: REQUIRED GRADIENT = 2.25 PERCENT
HORIZONTAL
DISTANCE
1500
HORIZONTAL
I 0
I 0.2
I
I 0.4
I 0.6
I
I 0.8
FROM
2000
I
35 FOOT
HEIGHT
2500
DISTANCE
I 1.0
FROM
I
I
1.2 HORIZONTAL
DISTANCE
POINT
(METERS)
3000
35 FOOT
HEIGHT
I 1.4 (NAUTICAL
= 350 FEET (107 m)
3500
POINT
I 1.6 MILES)
I
4000
4500
(FEET)
I 1.0
I 2.0
I
I 2.2
I
I 2.4
I
I 2.6
METRO III -ICAO TAKEOFF
FLIGHT
SECOND
SEGMENT
PATH
DISTANCE
TO 1500 FOOT
ACCELERATION r-----MAXIMUM
DISTANCE
HEIGHT
- DRY,
200
400
ANTI-ICE 600
(continued)
BLEED
NoTE ------q OAT WITH ENGINE ANTI-ICE ENGINE
0
ANNEX 8 AIR ON ON IS 5 C.
EFFECTS
(METERS) 800
1000
1200
1400
8,000
6,000
S.L. 0
1,000
2,000
3,000 4,000 (FEET) INCREASE IN ACCELERATION DISTANCE WITH ENGINE ANTI-ICE ON
5,000
FIGURE 4C-8 4C-20 8AC
PERFORMANCE
FAA
APPROVED: MAY 22189
METRO III -ICAO TAKEOFF SECOND
FLIGHT SEGMENT
ASSOCIATED
PATH DISTANCE ACCELERATION
ANNEX 8
TO 1500 FOOT HEIGHT (continued) DISTANCE - DRY, BLEED AIR ON
CONDITIONS:
EXAMPLE:
POWER . . . . .. . .. . . . . . . . . . . . . . . . . . . . . TAKEOFF (DRY) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG, ANTI-ICE . . . . . . . . . . . . OFF (SEE GRAPH) ACCELERATE TO V YSE . . . . . FIGURE 4F-1 GEAR . . . . . . . . . . .. . . . .. . .. . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . 114 (SEE NOTE)
GIVEN:
AIRPORT OAT = 10°C AIRPORT PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 kg) HEADWIND = 20 KNOTS VYSE CLIMB SPEED = 130 KIAS SECOND SEGMENT ACCELERATION DISTANCE = 6.200 FEET (1690 m)
OBTAIN:
7000
GROSS 6500
WEIGHT (KILOGRAMS) 6000 5500
5000 12
11
10
9
" 40
-20
0 AIRPORT
20
40
60
16,000
OAT (‘X2)
MAY 22189
14,000 GROSS
FIGURE FAA APPROVED:
15,000
13,000 WEIGHT
12.000 ( POUNDS)
11,000
10,000
0 WIND
10
20
30
(KNOTS)
4C-8 (continued)
PERFORMANCE
4C-2 1 8AC
METRO III -ICAO TAKEOFF FLIGHT THIRD SEGMENT
PATH CLIMB
DISTANCE GRADIENT
ANNEX 8
TO 1500 FOOT HEIGHT - DRY, BLEED AIR ON
(continued) ASSOCIATED
CONDITIONS:
POWER .. .... ... ... ... ... MAX CONTINUOUS GEN LOAD .. .... .... .... .... .... ... ... 3w AMPS BLEED AIR ..... ... ...... ... .... .... ... ..... ... .... . ON ENG ANTI-ICE .. .... .... OFF (SEE NOTE) CLIMB SPEED....V~SE (FIGURE 4F-1) GEAR .. ... .... ..... ... .... .... ... ...... ... .... .... ... ... UP FLAPS .... ... ..... .... ... .... ..... .... .... .... ... .... .. UP EXAMPLE: GIVEN:
OBTAIN:
AIRPORT OAT - 10% AIRPORT PRESSURE ALTITUDE - 2,UJO FEET GROSS WEIGHT - 14,OW POUNDS (6360 kg) HEADWIND = 20 KNOTS VYSE CLIMB SPEED - 130 KIAS THIRD SEGMENT CLIMB GRADIENT - 3.6 PERCENT
piiZZZ:y REDUCE
1
-4
-2
0
2
4 NET CLIMB
6 GRADIENT
FIGURE 4C-22 8AC
a (PERCENT)
10
CLIMB
* MAXIMUM
12
GRADIENT
OAT WITH
BY 2 0 PERCENT
ENGINE
14
ANTCICE
GRADIENT
ON IS 5%.
16
4C-9
PERFORMANCE
FAA APPROVED:
MAY 22l89
1
TAKEOFF DISTANT
FLIGHT PATH DISTANCE OBSTACLE CLEARANCE
ASSOCIATED
CONDITIONS:
EXAMPLE:
POWER ...................... MAX CONTINUOUS GEN LOAD ................................300 AMPS BLEED AIR ............................................ON ENG ANTI-ICE ......................ON OR OFF CLIMB SPEED.. ......VYSE (FIGURE 4F-1) GEAR ......................................................UP FLAPS .....................................................UP HORIZONTAL 0
2500
(continued)
TO 1500 FOOT HEIGHT - DRY, BLEED AIR ON
5000
DISTANCE 7500
GIVEN:
OBSTACLE HEIGHT ABOVE THE RUNWAY SURFACE = 700 FEET (213 m) OBSTACLE HORIZONTAL DISTANCE FROM END OF SECOND SEGMENT ACCELERATION = 15,000 FEET (4570 m) OBTAIN: REQUIRED GRADIENT = 2.0 PERCENT
FROM END OF SECOND SEGMENT ACCELERATION 10000 12500 15000
zm
POINT (METERS) 17500
20000
-I Jxl 0 -
22500
1,500
420
ic)
380
D 0 D 2 z m x 00
180
140
HORIZONTAL 0
1
2
3
DISTANCE 4
FROM END OF SECOND SEGMENT ACCELERATION
POINT (FEET)
5
9
HORIZONTAL
6
DISTANCE
7
(NAUTICAL
9
10
11
12
13
MILES)
..
_.--- -.
METRO III - ICAO ANNEX 8 SINGLE
ENGINE
TAKEOFF
RUN DISTANCE
MAXIMUM
- DRY, BLEED
OAT WITH ENGINE
TNOTEI
AIR ON
ANTI-ICE
ON IS 5°C.
ENGINE ANTI-ICE EFFECTS 0
(METERS) 150
100
50
200
250
300
8,000
6,000
S.L. 0
200
400
600
800
1,000
(FEET) INCREASE IN TAKEOFF RUN DISTANCE WITH ENGINE ANTI-ICE ON
FIGURE 4C-24 8AC
4C-11
PERFORMANCE
FAA APPROVED: MAY 22189 REVISED: MAR 18/92
METRO III - ICAO ANNEX 8 SINGLE
ENGINE ASSOCIATED
TAKEOFF
RUN DISTANCE
- DRY, BLEED
CONDITIONS:
AIR ON
EXAMPLE:
POWER ............................. TAKEOFF (DRY) GEN LOAD.. ............................... .300 AMPS BLEED AIR .............................................. ON ENG ANTI-ICE.. ........... OFF (SEE GRAPH) RUNWAY ................ DRY, HARD SURFACE V, ........................... FIGURE 4C-3 _ , SPEED.. -. --- ------VR SPEED .._......................... FIGURE 4C-3 V2 SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIGURE 4C-3 FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . . . .. . .. . . . .. . . . . .. . . 114 NOSE WHEEL STEERING . . ..ON OR OFF
MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE
GIVEN:
OBTAIN:
OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) Vi SPEED = 104 KlAs . .Vi SPEED = 109 KIAS V2 SPEED = 113 KIAS TAKEOFF RUN = 5,400 FEE T (1645 m)
kg)
EXCEED 4C-2. GROSS
WEIGHT
(1000
6
7
kg) 5
11
10 3
8
c
1
OAT (OC)
GROSS
WEIGHT
(1,000
POUNDS)
WIND
(KNOTS)
RUNWAY SLOPE (PERCENT)
FIGURE 4C-11 (continued) FAA APPROVED: MAR 18/92
PERFORMANCE
4C-25 8AC
METRO III - ICAO ANNEX 8 TWO ENGINE
RATE
OF CLIMB
AT V,, - DRY, BLEED
AIR ON ASSOCIATED
CONDITlONS:
POWER .... ....._...._........ MAX CONTINUOUS GEN LOAD .... ....._..................-.. 380 AMPS BLEED AIR .. .... ...I................................... ON ENG ANTI-ICE ... .... ..I.... OFF (SEE NOTE) CLIMB SPEED _......... VW (FIGURE 4’2-3) GEAR ... ..._......................-..................”..... UP FLAPS .. .... ..... .... ... .. .... .....-........................ II4
GIVEN: OBTAIN:
OAT - 10% PRESSURE ALTITUDE -4.000 FEET GROSS WEIGHT - 14,OW POUNDS (S350 $) VW CLIMB SPEED - 122 KlAS RATE OF CLIMB - 1900 FEET PER MINUTE TE
RATE OF CLIMB
I
4C-26 8AC
(FEET
PER MINUTE)
FIGURE 4C-12 PERFORMANCE
FAA APPROVED: MAR 18192